Comparison of Two- and Three-Dimensional Transonic Tests Made in Various Large Wind Tunnels

Abstract

A critical study is reported of testing conditions at transonic speeds and of the validity of the data obtained in various Wind-Tunnels. In two dimensional flow, two models of NACA 0012 and supercritical profiles have been tested as well as three homothetical profiles of NACA 0012. In three dimensional flow, four homothetical models of a typical transport aircraft were successively tested in twelve transonic tunnels commonly used for development tests in various countries. The data are compared in a broad range of Reynolds number (0.3 to 7 millions) between Mach number 0.7 and 0.96.

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Document Details

Document Type
Technical Report
Publication Date
Feb 10, 1976
Accession Number
ADA021348

Entities

People

  • Claude Armand
  • Maurice Bazin
  • Xavier Vaucheret

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Autonomy

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Ions
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Three Dimensional
  • Trailing Edges
  • Transonic Wind Tunnels
  • Transport Aircraft
  • Tunnels
  • Two Dimensional
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Modeling and Simulation
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